The WR/PWS peripheral monitoring and internal cycle tests
are used to detect transient failures.
By pressing the line key adjacent to the failure message,
the operator is allowed to the corresponding Trouble
Shooting Data. The peripheral monitoring and WR/PWS internal
cyclic tests are used to detect transient failures.
-TROUBLE SHOOTING DATA (Ref. Fig. 020A) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT.
-CLASS 3 FAULTS (Ref. Fig. 021) Allows to display the class 3 faults recorded during the last flight leg.
-GROUND REPORT (Ref. Fig. 021) Allows to present the class 1, 2 or 3 internal failures detected on ground. These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. By pressing the line key adjacent to the failure message, the operator is allowed to access to the corresponding Trouble Shooting Data.
-TEST (Ref. Fig. 022A, 023A, 024A) Allows a check of the correct operation of the WR/PWS on ground. This test can be performed through the CFDS by selecting on the MCDU the test function on the RADAR 1 main menu page. At the end of the BITE TEST, the test pattern comes into view. (Ref. Fig. 025A)
NOTE : If a failure of the windshear system is detected during the
____ BITE TEST, the windshear flags come into view. If the failure does not affect the radar mode, the test pattern stays available. If the failure affects the radar mode, nothing is shown.
All the information displayed on the MCDU during the BITE TEST configuration can be printed by the printer (Ref. 31-35-00). By pressing the line key adjacent to the internal failure message, the operator is allowed to access to the corresponding Trouble Shooting Data.
1EFF : 106-149, 201-299, 301-399, 1 34-41-00Page A16 1 1 Config-3 May 01/05 1 1 1CES 1R **ON A/C 001-049, 101-105, 151-199,
B. Self-Test (Ref. Fig. 025) A quick check of the correct operation of the WR/PWS installation can be performed by activating the test function:
-either through the CFDS by applying the Radar functional test procedure on the Multipurpose Control and Display Unit (MCDU)
- or by pressing the TEST pushbutton switch located on the face of the transceiver. When a fault is detected, it is stored and made available to the front panel Liquid Crystal Display (LCD) when the TEST pushbutton switch is pressed. The LCD is used as a maintenance aid to check the operational status of the WR/PWS. Once this TEST pushbutton switch is pressed, the LCD shows TEST IN PROGRESS. The self-test takes from 5 to 10 seconds to complete. At the end of the test, the LCD shows RADAR OK, INPUT OK if no faults were detected in either the radar or inputs connections. Pressing the return pushbutton switch enables access to the fault main menu.
* If radar faults were found during the self-test, the following
messages can be displayed:
R/T FAULT
ANT FAULT
CON FAULT
WG SWITCH FAULT
INDICATOR FAULT
COOLING FAULT
* If inputs faults were found during the self-test, the following messages can be displayed:
NO RAD ALT NO ALTITUDE IN NO AIR DATA IN
NO HEADING INPUT
1EFF : 001-049, 101-105, 151-199, 1 34-41-00Page A17 1 1 Config-3 May 01/05 1 1 1CES 1R Weather Radar - Dual Redundant Motor Antenna Drive R Figure 026
1EFF : 051-099, 1 34-41-00Page A18 1 1 Config-3 May 01/05 1 1 1CES 1 WEATHER RADAR SYSTEM - ADJUSTMENT/TEST
______________________________________
TASK 34-41-00-720-002
Functional test of the Tilt Control of the Weather-Radar Antenna Drive-Unit
WARNING : MAKE SURE THAT:
_______ -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA. -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135. ON EACH SIDE OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN ARC OF 90. ON EACH SIDE OF THE AIRCRAFT CENTERLINE.
1. Reason for the Job
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